Thus on a hot day(38'C) at 0.1 Mach

Thus on a hot day(38'C) at 0.1 Mach and 1.6-km pressure altitude, 0 = (38+273.1)/288.2 = 1.079, teta0= 1.079X1.002 = 1.081, g = 0.8256, g = 0.8256X1.007=0.8314, and the maximum mass flow through the 2-2m-diameter inlet is 704.6kg/sec.

Calculations
1. If the HP-1 starts out he the cruise at 11-km with a weight of 1,577,940 N, find the allowable TSFC for the distance of 10,650 km for the following cases.
a. Assume the aircraft performs a cruise climb (files at a constant Cd/Cl). what is its altitude at the end of the cruise climb?
b. Assume the aircraft cruises at a constant altitude of 11 km. Determine Cd/Cl at the start and end of cruise. Using the average of these two values, calculate the allowable TSFC.
2. Determine the loiter (endurance) mach numbers for altitudes of 10, 9, 8, 7, and 6 km when HP-1 aircraft is at 64 percent of Wro.
3. Determine the aircraft drag at the following points in the HP-1 aircraft's 11.120.-km flight based on the fuel consumptions listed above:
a. Takeoff, M = 0.23, sea level
b. Start of cruise, M = 0.83, 11 km
c. End of cruise climb, M = 0.83, altitude = ? ft
d. End of 11-km cruise, M = 0.83, 11 km
e. engine out (88 percent of Wto), M = 0.45,5 km

1-D2 GAS TURBINE DESIGN PROBLEM 2 (HF-1 AIRCRAFT)
Background
You are to determine the thrust and fuel consumption requirements of the two engines for the hypothetical fighter aircraft HF-1. This twin-engine fighter will supercruise at 1.6 Mach and will be capable of the following requirements:
1. Takeoff at maximum gross takeoff weight Wto from a 1200-ft (366-m) run way at sea level on a standart day.
2. Supercruise at 1.6 Mach and 40-kft altitude for 250 nmi (463 km) at 92 percent of Wto.
3. Perform 5g turns at 1.6 Mach and 30-kft altitude at 88 percent of Wto.
4. Perform 5g turns at 0.9 Mach and 30-kft altitude at 88 percent of wto.
5. Perform the maximum mission listed below.

all the data for the HF-1 contained in Example 1-2 apply. Preliminary mission analysis of the HF-1 using the methods of Ref. 12 for maximum mission gives the

Calculations
1. If the HP-1 starts out he the cruise at 11-km with a weight of 1,577,940 N, find the allowable TSFC for the distance of 10,650 km for the following cases.
 a. Assume the aircraft performs a cruise climb (files at a constant Cd/Cl). what is its altitude at the end of the cruise climb?
 b. Assume the aircraft cruises at a constant altitude of 11 km. Determine Cd/Cl at the start and end of cruise. Using the average of these two values, calculate the allowable TSFC.
2. Determine the loiter (endurance) mach numbers for altitudes of 10, 9, 8, 7, and 6 km when HP-1 aircraft is at 64 percent of Wro.
3. Determine the aircraft drag at the following points in the HP-1 aircraft's 11.120.-km flight based on the fuel consumptions listed above:
 a. Takeoff, M = 0.23, sea level
 b. Start of cruise, M = 0.83, 11 km
 c. End of cruise climb, M = 0.83, altitude = ? ft
 d. End of 11-km cruise, M = 0.83, 11 km
 e. engine out (88 percent of Wto), M = 0.45,5 km

1-D2 GAS TURBINE DESIGN PROBLEM 2 (HF-1 AIRCRAFT)
Background
You are to determine the thrust and fuel consumption requirements of the two engines for the hypothetical fighter aircraft HF-1. This twin-engine fighter will supercruise at 1.6 Mach and will be capable of the following requirements:
1. Takeoff at maximum gross takeoff weight Wto from a 1200-ft (366-m) run way at sea level on a standart day.
2. Supercruise at 1.6 Mach and 40-kft altitude for 250 nmi (463 km) at 92 percent of Wto.
3. Perform 5g turns at 1.6 Mach and 30-kft altitude at 88 percent of Wto.
4. Perform 5g turns at 0.9 Mach and 30-kft altitude at 88 percent of wto.
5. Perform the maximum mission listed below.

all the data for the HF-1 contained in Example 1-2 apply. Preliminary mission analysis of the HF-1 using the methods of Ref. 12 for maximum mission gives the

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Thus on a hot day(38'C) at 0.1 Mach and 1.6-km pressure altitude, 0 = (38+273.1)/288.2 = 1.079, teta0= 1.079X1.002 = 1.081, g = 0.8256, g = 0.8256X1.007=0.8314, and the maximum mass flow through the 2-2m-diameter inlet is 704.6kg/sec.Calculations1. If the HP-1 starts out he the cruise at 11-km with a weight of 1,577,940 N, find the allowable TSFC for the distance of 10,650 km for the following cases. a. Assume the aircraft performs a cruise climb (files at a constant Cd/Cl). what is its altitude at the end of the cruise climb? b. Assume the aircraft cruises at a constant altitude of 11 km. Determine Cd/Cl at the start and end of cruise. Using the average of these two values, calculate the allowable TSFC.2. Determine the loiter (endurance) mach numbers for altitudes of 10, 9, 8, 7, and 6 km when HP-1 aircraft is at 64 percent of Wro.3. Determine the aircraft drag at the following points in the HP-1 aircraft's 11.120.-km flight based on the fuel consumptions listed above: a. Takeoff, M = 0.23, sea level b. Start of cruise, M = 0.83, 11 km c. End of cruise climb, M = 0.83, altitude = ? ft d. End of 11-km cruise, M = 0.83, 11 km e. engine out (88 percent of Wto), M = 0.45,5 km 1-D2 GAS TURBINE DESIGN PROBLEM 2 (HF-1 AIRCRAFT)BackgroundYou are to determine the thrust and fuel consumption requirements of the two engines for the hypothetical fighter aircraft HF-1. This twin-engine fighter will supercruise at 1.6 Mach and will be capable of the following requirements:1. Takeoff at maximum gross takeoff weight Wto from a 1200-ft (366-m) run way at sea level on a standart day.2. Supercruise at 1.6 Mach and 40-kft altitude for 250 nmi (463 km) at 92 percent of Wto.3. Perform 5g turns at 1.6 Mach and 30-kft altitude at 88 percent of Wto.4. Perform 5g turns at 0.9 Mach and 30-kft altitude at 88 percent of wto.5. Perform the maximum mission listed below.all the data for the HF-1 contained in Example 1-2 apply. Preliminary mission analysis of the HF-1 using the methods of Ref. 12 for maximum mission gives the

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Sehingga pada hari yang panas (38'C) pada 0,1 Mach dan tekanan ketinggian 1,6 km-, 0 = (38 + 273,1) /288.2 = 1,079, teta0 = 1.079X1.002 = 1,081, g = 0,8256, g = 0.8256X1. 007 = 0,8314, dan aliran massa maksimum melalui inlet 2-2m-diameter adalah 704.6kg / sec. Perhitungan 1. Jika HP-1 dimulai ia pelayaran di 11-km dengan berat 1.577.940 N, menemukan diijinkan TSFC untuk jarak 10.650 km untuk kasus-kasus berikut. A. Asumsikan pesawat melakukan pendakian pesiar (file pada Cd konstan / Cl). apa yang ketinggiannya pada akhir pelayaran naik? b. Asumsikan kapal pesiar pesawat di ketinggian konstan 11 km. Tentukan Cd / Cl pada awal dan akhir pelayaran. Menggunakan rata-rata dari dua nilai, menghitung diijinkan TSFC. 2. Tentukan berkeliaran (daya tahan) nomor mach untuk ketinggian 10, 9, 8, 7, dan 6 km ketika HP-1 pesawat adalah pada 64 persen Wro. 3. Tentukan tarik pesawat pada titik-titik berikut di 11.120.-km penerbangan HP-1 pesawat ini didasarkan pada konsumsi bahan bakar yang tercantum di atas: a. Lepas landas, M = 0,23, permukaan laut b. Mulai dari kapal pesiar, M = 0.83, 11 km c. Akhir pelayaran pendakian, M = 0.83, ketinggian =? ft d. Akhir 11-km cruise, M = 0.83, 11 km e. mesin keluar (88 persen dari WTO), M = 0.45,5 km 1-D2 GAS TURBIN DESAIN MASALAH 2 (HF-1 PESAWAT) Latar Belakang Anda untuk menentukan dorong dan konsumsi bahan bakar persyaratan dari dua mesin untuk pesawat tempur hipotetis HF -1. Ini tempur bermesin ganda akan supercruise di 1,6 Mach dan akan mampu persyaratan sebagai berikut: 1. Lepas landas di lepas landas berat kotor maksimum WTO dari 1.200-ft (366 m) cara run di permukaan laut pada hari standart. 2. Supercruise di 1,6 Mach dan 40 k £ ketinggian untuk 250 nm (463 km) di 92 persen dari WTO. 3. Lakukan 5g ternyata di 1,6 Mach dan 30 k £ ketinggian di 88 persen dari WTO. 4. Lakukan 5g ternyata di 0,9 Mach dan 30 k £ ketinggian di 88 persen dari WTO. 5. Melakukan misi maksimum yang terdaftar di bawah ini. Semua data untuk-HF 1 yang terkandung dalam Contoh 1-2 berlaku. Analisis misi awal dari HF-1 menggunakan metode Ref. 12 untuk misi maksimal memberikan

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